RU2011138149A - ROTOR SECTION FOR TURBO MACHINE ROTOR, WORKING SHOVEL FOR TURBO MACHINE - Google Patents

ROTOR SECTION FOR TURBO MACHINE ROTOR, WORKING SHOVEL FOR TURBO MACHINE Download PDF

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Publication number
RU2011138149A
RU2011138149A RU2011138149/06A RU2011138149A RU2011138149A RU 2011138149 A RU2011138149 A RU 2011138149A RU 2011138149/06 A RU2011138149/06 A RU 2011138149/06A RU 2011138149 A RU2011138149 A RU 2011138149A RU 2011138149 A RU2011138149 A RU 2011138149A
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Russia
Prior art keywords
rotor
blade
leg
working
hole
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RU2011138149/06A
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Russian (ru)
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RU2486348C2 (en
Inventor
Гуидо АХАУС
Аксель БУШМАНН
Саша ДУНГС
Харальд ХЕЛЛЬ
Карстен КОЛЬК
Мирко МИЛАЗАР
Петер ШРЕДЕР
Вячеслав ФАЙТСМАН
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Сименс Акциенгезелльшафт
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B21/00—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings
    • F16B21/02—Releasable fastening devices locking by rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B21/00—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings
    • F16B21/02—Releasable fastening devices locking by rotation
    • F16B21/04—Releasable fastening devices locking by rotation with bayonet catch
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1. Секция (10) ротора для ротора турбомашины, на наружном периметре которой предусмотрены распространяющиеся в осевом направлении ротора крепежные пазы (16) для рабочих лопаток, в каждом из которых установлена одна рабочая лопатка (18) ножкой (20) лопатки, соответствующей крепежному пазу (16) для рабочей лопатки,включающая в себя предусмотренные на рабочих лопатках (18) обращенные радиально внутрь контактные поверхности (34),причем для пропускания охлаждающего средства по торцевой поверхности (28) ротора пластинчатые уплотнительные элементы (30) под действием центробежной силы прилегают к контактной поверхности (34), причем для фиксации уплотнительных элементов (30) от смещения в окружном направлении по меньшей мере один из уплотнительных элементов (30) снабжен предусмотренным в этом уплотнительном элементе (30) отверстием (44), служащим для помещения блокировочного элемента (46, 62),причем предусмотрено соосное отверстию (44) гнездо (58) и установленный в гнезде (58) и в отверстии (44) с зафиксированным положением блокировочный элемент (46, 62),отличающаяся тем,что гнездо (58) расположено в ножке (20) лопатки и отверстие (44) выполнено подобно замочной скважине, а блокировочный элемент (46) выполнен в виде пальца с расположенным на его наружном периметре кулачком (50), который может ввертываться между ножкой (20) лопатки и уплотнительным элементом (30).2. Секция (10) ротора по п.1, у которой каждое гнездо (58) расположено ближе к обращенной радиально внутрь контактной поверхности (34), а отверстие (44) расположено ближе к тому краю (32) уплотнительного элемента (30), который прилегает к контактной поверхности (34) рабочей лопатки (18), чем к внутреннему краю (36) упло1. Section (10) of the rotor for the rotor of the turbomachine, on the outer perimeter of which are provided the mounting grooves (16) extending in the axial direction of the rotor for the working blades, each of which has one working blade (18) with a blade leg (20) corresponding to the mounting groove (16) for a working blade, which includes contact surfaces (34) that are provided on the working blades (18) and radially inwardly contacted, and for passing the cooling medium along the end surface (28) of the rotor, plate sealing elements (30) under the action of centrifugal force is adjacent to the contact surface (34), and to fix the sealing elements (30) from displacement in the circumferential direction, at least one of the sealing elements (30) is provided with an opening (44) provided for this sealing element (30), which serves to the premises of the locking element (46, 62), and provided with a coaxial hole (44) socket (58) and installed in the socket (58) and in the hole (44) with a fixed position, the locking element (46, 62), characterized in that the socket ( 58) located in the leg (20) of the lop and a heel opening (44) formed like a keyhole, a lock member (46) is in the form of a finger placed on its outer periphery a cam (50) which can screw-in between the foot (20) of the blade and the sealing member (30) .2. The rotor section (10) according to claim 1, in which each socket (58) is located closer to the radially inward contact surface (34), and the hole (44) is located closer to the edge (32) of the sealing element (30), which is adjacent to the contact surface (34) of the working blade (18) than to the inner edge (36)

Claims (15)

1. Секция (10) ротора для ротора турбомашины, на наружном периметре которой предусмотрены распространяющиеся в осевом направлении ротора крепежные пазы (16) для рабочих лопаток, в каждом из которых установлена одна рабочая лопатка (18) ножкой (20) лопатки, соответствующей крепежному пазу (16) для рабочей лопатки,1. Section (10) of the rotor for the rotor of the turbomachine, on the outer perimeter of which are provided the mounting grooves (16) extending in the axial direction of the rotor for the working blades, each of which has one working blade (18) with a blade leg (20) corresponding to the mounting groove (16) for the working blade, включающая в себя предусмотренные на рабочих лопатках (18) обращенные радиально внутрь контактные поверхности (34),including contact surfaces (34) provided on the working blades (18), radially inwardly facing, причем для пропускания охлаждающего средства по торцевой поверхности (28) ротора пластинчатые уплотнительные элементы (30) под действием центробежной силы прилегают к контактной поверхности (34), причем для фиксации уплотнительных элементов (30) от смещения в окружном направлении по меньшей мере один из уплотнительных элементов (30) снабжен предусмотренным в этом уплотнительном элементе (30) отверстием (44), служащим для помещения блокировочного элемента (46, 62),moreover, to pass the coolant along the end surface (28) of the rotor, the plate sealing elements (30) are attached to the contact surface (34) under the action of centrifugal force, and at least one of the sealing elements is used to fix the sealing elements (30) from displacement in the circumferential direction (30) is provided with an opening (44) provided in this sealing element (30), which serves to place the blocking element (46, 62), причем предусмотрено соосное отверстию (44) гнездо (58) и установленный в гнезде (58) и в отверстии (44) с зафиксированным положением блокировочный элемент (46, 62),moreover, a coaxial hole (44) is provided for the socket (58) and a blocking element (46, 62) installed in the socket (58) and in the hole (44) with a fixed position, отличающаяся тем,characterized in что гнездо (58) расположено в ножке (20) лопатки и отверстие (44) выполнено подобно замочной скважине, а блокировочный элемент (46) выполнен в виде пальца с расположенным на его наружном периметре кулачком (50), который может ввертываться между ножкой (20) лопатки и уплотнительным элементом (30).that the socket (58) is located in the leg (20) of the blade and the hole (44) is made like a keyhole, and the locking element (46) is made in the form of a finger with a cam (50) located on its outer perimeter, which can be screwed between the leg (20) ) blades and sealing element (30). 2. Секция (10) ротора по п.1, у которой каждое гнездо (58) расположено ближе к обращенной радиально внутрь контактной поверхности (34), а отверстие (44) расположено ближе к тому краю (32) уплотнительного элемента (30), который прилегает к контактной поверхности (34) рабочей лопатки (18), чем к внутреннему краю (36) уплотнительного элемента (30).2. The rotor section (10) according to claim 1, in which each socket (58) is located closer to the radially inward contact surface (34), and the hole (44) is located closer to that edge (32) of the sealing element (30), which is adjacent to the contact surface (34) of the working blade (18) than to the inner edge (36) of the sealing element (30). 3. Секция (10) ротора по п.1 или 2, у которой блокировочный элемент (46) с торцевой стороны снабжен зубцом (56), который может загибаться в отверстие (47) под бородку ключа отверстия (44), подобного замочной скважине.3. The rotor section (10) according to claim 1 or 2, in which the blocking element (46) is provided on the front side with a tooth (56), which can be bent into the hole (47) under the key of the hole (44), similar to a keyhole. 4. Секция (10) ротора по п.3, у которой зубец (56) является частью торцевого венца (52) блокировочного элемента (46).4. The rotor section (10) according to claim 3, in which the tooth (56) is part of the end ring (52) of the locking element (46). 5. Секция (10) ротора по п.1, у которой блокировочный элемент (62) зафиксирован от выпадения посредством Z-образной фиксирующей пластинки (66), первый конец которой прилегает между уплотнительным элементом (30) и торцевой стороной (26) ножки (20) лопатки.5. The rotor section (10) according to claim 1, in which the locking element (62) is secured against falling out by means of a Z-shaped fixing plate (66), the first end of which abuts between the sealing element (30) and the end face (26) of the leg ( 20) scapula. 6. Секция (10) ротора по одному из пп.1, 2, 4 или 5, у которой блокировочный элемент (46, 62) снабжен торцевым отверстием, служащим для демонтажа.6. Section (10) of the rotor according to one of claims 1, 2, 4 or 5, in which the blocking element (46, 62) is equipped with an end hole that serves for dismantling. 7. Секция (10) ротора по п.3, у которой блокировочный элемент (46, 62) снабжен торцевым отверстием, служащим для демонтажа.7. Section (10) of the rotor according to claim 3, in which the blocking element (46, 62) is equipped with an end hole serving for dismantling. 8. Секция (10) ротора по одному из пп.1, 2, 4, 5 или 7, у которой уплотнительные элементы (30) в окружном направлении, прилегая друг к другу, образуют кольцевое уплотнение, установленное в кольцевом пазу (38), который предусмотрен на окружной поверхности, расположенной на торцевой боковой поверхности ротора.8. The rotor section (10) according to one of claims 1, 2, 4, 5 or 7, in which the sealing elements (30) in the circumferential direction, abutting against each other, form an annular seal installed in the annular groove (38), which is provided on a circumferential surface located on the end side surface of the rotor. 9. Секция (10) ротора по п.3, у которой уплотнительные элементы (30) в окружном направлении, прилегая друг к другу, образуют кольцевое уплотнение, установленное в кольцевом пазу (38), который предусмотрен на окружной поверхности, расположенной на торцевой боковой поверхности ротора.9. The rotor section (10) according to claim 3, in which the sealing elements (30) in the circumferential direction, abutting against each other, form an annular seal installed in the annular groove (38), which is provided on the circumferential surface located on the end side rotor surface. 10. Секция (10) ротора по п.6, у которой уплотнительные элементы (30) в окружном направлении, прилегая друг к другу, образуют кольцевое уплотнение, установленное в кольцевом пазу (38), который предусмотрен на окружной поверхности, расположенной на торцевой боковой поверхности ротора.10. The rotor section (10) according to claim 6, in which the sealing elements (30) in the circumferential direction, abutting against each other, form an annular seal installed in the annular groove (38), which is provided on the circumferential surface located on the end side rotor surface. 11. Рабочая лопатка (18) для турбомашины, включающая в себя елкообразную или молоткообразную ножку (20) лопатки, к которой примыкает платформа (22), а к ней аэродинамически изогнутая рабочая часть (60) лопатки, и снабженная выдающимся за ножку (20) лопатки выступом, при этом на обращенной к ножке (20) лопатки нижней стороне выступа предусмотрена обращенная к ножке (20) лопатки контактная поверхность (34) для пластинчатого уплотнительного элемента (30), отличающаяся тем, что11. The working blade (18) for the turbomachine, which includes a Christmas tree or hammer-shaped leg (20) of the blade, to which the platform (22) adjoins, and to it the aerodynamically curved working part (60) of the blade, and provided with a protruding leg (20) the blades by a protrusion, while on the bottom side of the protrusion facing the leg (20) of the blade, a contact surface (34) for the plate sealing element (30) facing the leg (20) of the blade, characterized in that непосредственно рядом с выступом предусмотрено выполненное в виде глухого отверстия гнездо (58) в торцевой стороне (26) ножки (20) лопатки, предназначенное для помещения блокировочного элемента (46, 62).Immediately next to the protrusion, a socket (58) is provided in the form of a blind hole in the end side (26) of the blade leg (20), designed to accommodate the blocking element (46, 62). 12. Рабочая лопатка (18) по п.11, у которой гнездо (58) расположено ближе к выступу, чем к нижней стороне ножки (20) лопатки.12. The working blade (18) according to claim 11, in which the socket (58) is located closer to the protrusion than to the lower side of the blade legs (20). 13. Рабочая лопатка (18) по п.11 или 12, у которой контактная поверхность (34) по меньшей мере частично выполнена в виде дна паза, открытого в направлении ножки (20) лопатки.13. The working blade (18) according to claim 11 or 12, in which the contact surface (34) is at least partially made in the form of a bottom of the groove open in the direction of the blade leg (20). 14. Рабочая лопатка (18) по п.11 или 12, у которой выступ выполнен в виде части платформы (22) или части отстоящей сбоку уплотнительной лопасти.14. The working blade (18) according to claim 11 or 12, in which the protrusion is made in the form of part of the platform (22) or part of the sealing blade that is spaced apart from the side. 15. Рабочая лопатка (18) по п.13, у которой выступ выполнен в виде части платформы (22) или части отстоящей сбоку уплотнительной лопасти. 15. The working blade (18) according to item 13, in which the protrusion is made in the form of part of the platform (22) or part of the sealing blade that is spaced apart from the side.
RU2011138149/06A 2009-02-17 2010-01-27 Section of rotor for turbomachine; rotating blade for turbomachine RU2486348C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09002223.7 2009-02-17
EP09002223A EP2218873A1 (en) 2009-02-17 2009-02-17 Rotor section for a rotor of a turbo machine, rotor blade for a turbo machine and blocking element
PCT/EP2010/050934 WO2010094539A1 (en) 2009-02-17 2010-01-27 Rotor section for a rotor of a turbomachine, rotor blade for a turbomachine

Related Child Applications (1)

Application Number Title Priority Date Filing Date
RU2012103315/06A Division RU2518749C2 (en) 2009-02-17 2012-01-31 Turbomachine rotor section

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RU2011138149A true RU2011138149A (en) 2013-03-27
RU2486348C2 RU2486348C2 (en) 2013-06-27

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RU2011138149/06A RU2486348C2 (en) 2009-02-17 2010-01-27 Section of rotor for turbomachine; rotating blade for turbomachine
RU2012103315/06A RU2518749C2 (en) 2009-02-17 2012-01-31 Turbomachine rotor section

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US (2) US8894371B2 (en)
EP (3) EP2218873A1 (en)
JP (2) JP5276182B2 (en)
KR (2) KR101662351B1 (en)
CN (2) CN102317577B (en)
BR (2) BRPI1008928B8 (en)
CA (2) CA2752666C (en)
ES (2) ES2527005T3 (en)
MX (2) MX2011008672A (en)
PL (2) PL2399004T3 (en)
RU (2) RU2486348C2 (en)
WO (1) WO2010094539A1 (en)

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8888455B2 (en) * 2010-11-10 2014-11-18 Rolls-Royce Corporation Gas turbine engine and blade for gas turbine engine
EP2514923A1 (en) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Screen device, integrated bladed rotor base body, method and fluid flow engine
US9334738B2 (en) * 2012-10-23 2016-05-10 Siemens Aktiengesellschaft Gas turbine including belly band seal anti-rotation device
JP5358031B1 (en) 2013-03-22 2013-12-04 三菱重工業株式会社 Turbine rotor, turbine, and seal plate removal method
EP2860349A1 (en) 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Turbine blade and gas turbine
EP2860350A1 (en) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Turbine blade and gas turbine
EP2860351A1 (en) 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Assembly for securing a function position of a side plate on a rotor disk arranged relative to a rotor blade assembled on the rotor disk
CN103700413B (en) * 2013-12-20 2016-04-06 中广核核电运营有限公司 The tripping device of reactor core internal upper part component and fuel assembly bite
EP2933436A1 (en) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Wheel disc with at least one sealing sheet metal panel
EP2952688A1 (en) * 2014-06-02 2015-12-09 Siemens Aktiengesellschaft Method for assembling a stator stage of a gas turbine engine
EP3015656A1 (en) * 2014-10-30 2016-05-04 Siemens Aktiengesellschaft Wheel disc assembly
US10047865B2 (en) 2015-12-07 2018-08-14 General Electric Company Steam turbine rotor seal radial key member, related assembly and steam turbine
US10036270B2 (en) 2015-12-07 2018-07-31 General Electric Company Steam turbine rotor seal key member, related assembly and steam turbine
US10036268B2 (en) * 2015-12-07 2018-07-31 General Electric Company Steam turbine rotor seal sliding key member, related assembly and steam turbine
US10087768B2 (en) 2015-12-07 2018-10-02 General Electric Company Steam turbine rotor seal key member, related assembly and steam turbine
US10196916B2 (en) 2016-04-08 2019-02-05 Siemens Aktiengesellschaft Rotor disk having an end-side sealing element
WO2017174723A1 (en) 2016-04-08 2017-10-12 Siemens Aktiengesellschaft Rotor disk having an end-face sealing element
DE102016205921B4 (en) 2016-04-08 2019-04-25 Siemens Aktiengesellschaft Rotor disc arrangement with two-part seal
DE102016208759A1 (en) 2016-05-20 2017-11-23 Siemens Aktiengesellschaft Rotor disc with front-side sealing element
DE102018101836B4 (en) * 2018-01-26 2023-05-04 Airbus Operations Gmbh Fastening system for fastening components in a vehicle
EP3564489A1 (en) * 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor with for centrifugal forces optimized contact surfaces
FR3081916B1 (en) * 2018-06-04 2020-09-11 Safran Aircraft Engines MOBILE WHEEL FOR AIRCRAFT TURBOMACHINE, INCLUDING AN AXIAL RETENTION RING FIXED TO THE DISC BY AT LEAST ONE LOCKING SYSTEM
EP3611344A1 (en) 2018-08-16 2020-02-19 Siemens Aktiengesellschaft Rotor with peripheral securing of sealing elements
KR102142141B1 (en) 2018-08-17 2020-08-06 두산중공업 주식회사 Turbine, gas turbine, and disassembling method of turbine blade
KR102134812B1 (en) * 2018-08-17 2020-07-16 두산중공업 주식회사 Turbine, gas turbine including the same, assembling method of turbine, and disassembling method of turbine
FR3091722B1 (en) * 2019-01-11 2020-12-25 Safran Aircraft Engines Rotor, turbine equipped with such a rotor and turbomachine equipped with such a turbine
CN110454233A (en) * 2019-08-08 2019-11-15 中国长江动力集团有限公司 A kind of steam turbine is cultivated one's moral character the movable vane piece group of blade and its composition
JP7213835B2 (en) * 2020-02-10 2023-01-27 三菱重工業株式会社 turbine wheel
KR102400013B1 (en) * 2020-08-21 2022-05-18 두산에너빌리티 주식회사 Assembling structure of compressor blade seal and Gas turbine comprising the same and Assembling method of compressor blade seal
CN113494522A (en) * 2021-07-20 2021-10-12 人本股份有限公司 Rolling bearing capable of automatically eliminating installation inclination angle
EP4198322A1 (en) * 2021-12-15 2023-06-21 Erbe Elektromedizin GmbH Rotary connector
CN116608011A (en) * 2022-02-15 2023-08-18 斗山恒能有限公司 Gas seal assembly structure of turbine blade and gas turbine

Family Cites Families (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3076634A (en) * 1959-06-12 1963-02-05 Ass Elect Ind Locking means for compressor and turbine blades
US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US3720480A (en) * 1971-06-29 1973-03-13 United Aircraft Corp Rotor construction
US3748060A (en) 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
US4344740A (en) 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
JPS5835203A (en) 1981-08-28 1983-03-01 Hitachi Ltd Bucket locking mechanism
FR2521656A1 (en) * 1982-02-12 1983-08-19 Huret & Fils DEVICE FOR FIXING THE TWO WINGS OF A CRANKSET FOR A BICYCLE
RU1077380C (en) 1982-03-22 1995-06-19 Запорожское машиностроительное конструкторское бюро "Прогресс" Working wheel for turbomachine
FR2524933B1 (en) 1982-04-13 1987-02-20 Snecma AXIAL LOCKING DEVICE FOR TURBINE OR COMPRESSOR ROTOR BLADES
JPH0611683Y2 (en) 1987-01-27 1994-03-30 津田駒工業株式会社 Tailstock with indexing function
SU1714170A1 (en) * 1990-02-23 1992-02-23 Ленинградский Кораблестроительный Институт Arrangement to lock working blades of turbine against axial displacement
JPH0611683B2 (en) 1990-07-09 1994-02-16 富士システムズ株式会社 Dental adhesive
DE19757188A1 (en) * 1997-12-22 1999-06-24 Asea Brown Boveri Single-stage axial turbine blade fixing device
IT1311292B1 (en) * 1999-12-29 2002-03-12 Sila Holding Ind S R L RETAINING GROUP OF A STRETCHED ELEMENT PARTICULARLY OF THE AGUAINA OF A FLEXIBLE CABLE.
EP1389669B1 (en) * 2002-08-16 2006-06-07 Siemens Aktiengesellschaft Fastening system
UA57357C2 (en) * 2002-09-05 2005-02-15 State Entpr Zaporizhzhya Akade Working wheel of axial turbo-machine
RU62165U1 (en) * 2006-11-15 2007-03-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" DEVICE FOR FIXING BLADES IN A RING groove of a DRIVER WHEEL DISC
EP1944472A1 (en) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Axial rotor section for a rotor in a turbine, sealing element for a turbine rotor equipped with rotor blades and rotor for a turbine
ATE439922T1 (en) * 2007-01-09 2009-09-15 Siemens Ag BENDING DEVICE FOR BENDING A LOCK PLATE OF A ROTOR OF A TURBINE
PL1944471T3 (en) * 2007-01-09 2010-02-26 Siemens Ag Axial rotor section for a rotor in a turbine
EP1978211A1 (en) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Assembly for axial protection on rotor blades in a rotor and gas turbine with such an assembly
EP1977861A1 (en) * 2007-04-05 2008-10-08 Siemens Aktiengesellschaft Multi-part pin remover for removing a pin or bolt from the hole of a component part
US7806662B2 (en) * 2007-04-12 2010-10-05 Pratt & Whitney Canada Corp. Blade retention system for use in a gas turbine engine
US20090148298A1 (en) * 2007-12-10 2009-06-11 Alstom Technologies, Ltd. Llc Blade disk seal
US8007230B2 (en) * 2010-01-05 2011-08-30 General Electric Company Turbine seal plate assembly
US8459953B2 (en) * 2010-01-19 2013-06-11 General Electric Company Seal plate and bucket retention pin assembly

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